Aeroplane.



B. L. MARENESS.

AEROPLANE.

APPLICATION FILED N0v.21. 1910.

hmmwam Patented; July 6,1915.

2 SHEETS-SHEET 1.

f a I 9 9 I Maw 2250/ B; L. MARENESS.

AERQPLANE.

APPLICATION FILED NOV.2l 1910.

Patented July 6, 1915.

2 SHEETS-SHEET 2.

Va ley/2% nected with the motor in the usual way and is located at the extreme forward end of the To all whom it may concern Be it known that 1, Barron L. H L

a citizenof the United States, and resident of Chicago, Illinois, have invented a new and useful Improvement in Aeroplanes, of which the following is a specification.

My invention relates to aeroplanes particularly of the mono lane type and the preferable form may termed a mono-ovalplane.

Une of the objects of my invention is the provision of improved means for maintain ing the lateral balance of an aeroplane.

A further object -of my invention is the provision of improved steering means for an aeroplane. I

I will describe the principles of m invention and the means for embodying t e'same and particularly point out the features thereof in the appendm claims.

In the accompanying drawings-Figure 1 represents a plan view of an aeroplane embodying my invention; Fig. 2 represents a front end view of Fig. 1; Fig. 3 represents an end view of the tubes and the mechanism for operating the sections thereof; Fig. 4 is an end view of the right hand portion of Fig. 3; Figs. 5 and 6 are detail views of the mechanism for operating the elevating rudder; Fig; 7 is a .side View of the elevating rudder and direction rudder, showing their relative location and the connection between the two.v

Referring to Fig. 1, it will be seen that the motor 1 ismounted at the forward end of the frame 2, although it may have any other desired location.

3 designates the propeller which is conframe 2.

Connected to the frame 2, at an intermediate portion so as to be rigid therewith, are the laterally extending aeroplanes or Wings 4, 5, which are horizontal at their outer ends at 6 and 7 respectively and are also'horizontal at their, forward ends at 8 and 9.

These wings or planes are curved toward the rear with a gradually increasing curvature from the outermost ends,'at 6 and 7, to the frame 2, at 10 and 11.

12 designates the rudder mechanism which comprises a direction rudder 13 and an elevating rudder 14, the formerbeing located ahead of the latter, as shown in Fig. 1. The direction rudder 13 is connected to the frame Specification of Letters Patent. application filed November at, 1am Serial No. mama.

tilted at an Patented duly d, ltd;

when the direction rudder is turned, the

elevating rudder will be turned with it, although the elevating rudder may also be time desired.

Intermediate the rudder mechanism 12 and thewings at, 5 is a balancing plane 15 which is rigidly connected to the frame 2 and extends laterally therefrom occupying a horizontal position and being in size considerably smaller in area than the combined area of the wings 4r, 5. This balancing plane may be curved downwardly similarly to the innerends of the wings a, 5, as indicated at 10 and ll.

The seat 16 for the operatormay belocated in the frame work 2 between the balancing plane 15 and the wings of the aeroplane, the seat bein in a convenient position with respect to ,t e steering wheel 17, the foot lever 18 and the controlling mechanism for the motor 1.

At the outer ends of the wings i, 5 l have shown tubes 19 and 20 which may be circular in cross section, or oval in cross section, as shown in Fig. 3, or otherwise shaped so long as they extend in a longitudinal direction and are open at both ends so as to afford air passages at the tips of the wings 4t and 5. These tubes may be located so that the horizontal plane to their axes will coincide with the horizontal planes of the wings 6 and 7, as arran ed in Fig. 2, or the tubes may be above or elow'that location, or one above and the other below. The tubes at dill the tips of the wings arranged longitudinall'y for the passage of air through the same during the flight of the aeroplane, are for the purpose of maintaining the horizontal planes of the aeroplane with respect to forward or rearward tilting, althou h they also assist in maintaining lateral alarms and in counteracting any tendency of the aeroplane to tip sidewise. The effect of the tubes is such that if the aeroplane is in flight and the motor should happen to stop, the aeroplane can not dive forward to the earth to destruction but will descend while in a substantially horizontal position and therefore will descend gently by reason of the parachute action of the various planes which are thus maintained in substantially horizontal positions.

The monoplanes and tubes may beheld in proper position and in a stabile structure by means of the usual tie wires and braces. The

. landing.

' The longltudinally extending'tubes at the wingtips are made up of longitudinal sections, as illustrated in Figs. 3 and 4. The

uppe i ly connected to the framework of the aeroplane, but the lateral sections 23 and 24 and J' r and lower sections 21 and 22 are rig- 25, 26 are movable. The sections 23' and 25 are'respectively pivoted, at 27 and 28, to the fixed section 21 and springs 29 and 30 act on these sections tending to close them when released. The movable sections 24 and 26 are pivoted respectively at 31 and 32 to the fixed section 22 and springs 33, 34 act on the movable sections 24 and-26 tending to close them when released.

The. actuating mechanism for operating the movable section of the tubes, is such that by a single manual actuation all the sections of both tubes may be brought to the position shown at the right hand portion of Fig. 3, and when released they will automatically return to initial position so as to again form closed tubes, or all of the sections of one tube may be opened or only the outermost sections of one of the tubes may be opened, as shown in Fig. .4. The actuating mechanism for operating all the sections of both tubes at the same time, comprises the wheel. 17 which when turned will oscillate the inclined rod 35 which extends through the fixed tubular support 36, as shown in Fig. 5.

When the rod 35 is oscillated, the lever 36, shown in Fig. 3, is likewise turned to exert the pull on the wires 37 and 38fwhich effects the turningof the levers 39' and 40 which are pivoted to a part of the framework 2.

. When the levers 39 and 40 are thus turned,

motion will be transmitted to the movable sections of both of the tubes to the position shown in dotted lines at the right hand portion of Fig. 3. A form of mechanism which may be used for transmitting motion to the movable sections is illustrated more clearly in Fig. 4, by reference to which it "will be seen that the ends of the lever 40 are connected by the links 41 and 42 to disks 43 and 44, respectively, which slide on the Y rod 2' and push against the disks 45 and 46 which also slide on the rod 2. The disks 45 and 46 are respectively connected by links 47, 47 and 48, 48 to the movable sections 25, 26 and 23, 24. It will be evident that when the lever 40 is turned clockwise, the disks 45 and 46 will be pushed farther apart and therefore the movable sections of the tube will be pushed to some position as shownby the dotted lines in Fig. 4, or some intermediate position depending upon the 5 extent to which the wheel 17 is turned.

movable sections to initial position. If desired, these springs may be differently located so as to act on the disks 45 and 46 direct or the arrangement may be such that the movable sections are positively pulled back to imtial position when the wheel 17 is returnmg to initialposition. Now when it is desired to open only one of the tubs by operatmg all of the movable sections thereof, the-lever 49 may be actuated by the operator. This lever is pivoted at 50 to the framework 2 and is connected at 51 to a wire 52 which is connected to the wire 38 at 53. It will be evident that if the lever 49, as vrewedinFig. 3, is moved to the left, the wire 52 will exert the pull on a-portion of the wire 38 to turn the lever 40 and thus spread apart'both the disks 45 and 46- and open the tube sections 23, 24, 2 5 and 26, as

Fig. 3, are to be opened, the lever 49' may be actuated to exert the pull on the wire 52 to the. right. Now if it is desired to move only the outermost sections of the right hand tube, as viewed in Fig. 3, the lever 54, which is pivoted at 55 to the frame 2, may be moved to the right thus exerting a pull on the wire 56 and pulling. the disk 45 to the dotted line position shown in Fig. 4. Suitable direction pulleys 57, 58 may be mounted on the frame-work to properly guide the wire 56. It will be seen that in order to secure the opening of the outermost movable sections to the position shown in dotted lines in' Fi 4, the lever 54 is moved toward the rig t. Upon movement of the lever 54 to the left the inner movable sections 23 and 24 could be opened while the outermost sections remain closed. In a similar manner, the tube at the left in Fig. 3, can have its outermost sections opened by moving the lever 54 to the left and its inner by the wires 60, 60' to the lever 18 which may be operated by the feet of the operator, the lever 18 being pivoted at its mid-point to the frame-work 2. It will be observed nil tacos i that the post 61 which carries the direction rudder 13 also carries the frame-work 62 of the elevating plane 14 so that when the d1- rection rudder is turned, the elevating plane is turned in a horizontal direction with it. Inv order to tilt the elevating plane, I have arrangedthe wheel 17 and the connections between the same and the elevatlng rudder m such a manner that when the tube 63 is pulled upwardly by means of the wheel 17, the aeroplane will be directed upwardly and when the tube 68 is pushed downwardly by the wheel 17, the aeroplane will be directed downwardly.

64 designates collars which are fixed to the tube 63 and 65 is a loose ringbetwee'n f the collars 64 so thatthe wheel 17 maybe turned without adecting the-connections to the elevating rudder. The ring 65 18 con neeted by the link 66 to the bell crank lever 67 which is pivoted to the frame work 2. At the other ends of the double bell crank 67 are wires 68 and 69 which are connected to the lever 70 which ispivoted'at 71130 the direction rudder and turn the horizontal rudder with it. In this way the direction of the course of flight can be changed as desired and by reason of the turning of the horizontal rudder with the direction rudder, a better lateral balance of the aeroplane may be maintained and the. upward or downward direction of the aeroplane better controlled. The arrangement is such that whether the directionrudder is turned from its position shown in Fig. 1, or not, the elevation rudder may betilted forward or backward by means of the operating lever 17. In order to avoid mistakes in the proper actuation of the elevating rudder, I prefer to arrange the connections between the wheel 17 and the elevating rudder, so that when the wheel is pushed down, the aeroplane will bedirected downwardly and when the wheel-l7 is pulled up, the aeroplane will be directed upwardly.

Having thus described the principles of operation of my invention, together with one mechanism for carrying the same into efl'ect, I wish it to be understood that many changes in the details might readily suggest themselves to persons skilled in the art without departing from the spirit and scope of my invention as defined by the claims and I therefore consider it unnecessary to encumber the specification with a recitation of all of them. I wish therefore not to be restricted to the precise construction herein disclosed.

What I claim and desire to secure by Letters Patent of the United States is 1. In an aeroplane, the combination of a sustaining plane, and balancing tubes connected to said plane, said tubes being divided into longitudinal relatively movable sections.

2. In an areoplane, the combination with frame-work, of sustaining planes, a tube having a longitudinal movable section extending throughout its entire length, and means for moving said section to diderent positions.

3. In an aeroplane, the combination with a lifting plane, of a plurality of longitudinally-extending open-ended tubes formin the lateral terminals of the aero lane an each being provided with l'ongitu inal movable sections extending throughout the entire length of. said tubes and means for operating said sections to various positions.

4. The combination with an aeroplane, of

sectional tubes one at each lateral end of said aeroplane, and means for actuating the movable sections of said tubes to open or close the same.

5. The combination in an aeroplane, of lateral 'end tubes each open at both ends and comprising movable sections, and means for movirlz some or all of the movable sections at wi 6. The combination with a mono-ovaling provided with a plurality of longitudinal sections, and means for operating said 2 sections to predetermined positions.

7. In an aeroplane, the combination with framework, of lifting planes carried thereby, a pair of tubes one atthe outer extremity of each of said lifting planes and each extending longitudinally and being open from end to end for free movement of air therethrough, portions of the walls of said tubes being adapted to be changed in position with respect to other portions thereof.

8. In an aeroplane, the combination with a frame, of lifting planes rigidly connected thereto, and sectional tubes carried bysaid planes, said tubes being open from end to end for free movement of air therethrough and the sections being adjustable to different positions.

9. In an aeroplane, the combination with p a frame, of lifting planes rigid therewith,

of sectional tubes, and means for moving the sections of one of said tubes independently of the sections of the other.

- 12.; The combination with an aero lane,

of sectional tubes, means for moving a the sections of said tubes, means for moving all the sections of eitherv of said tubes, and

means'for moving only some of the sections of either of said tubes. y

13., lhe combination of an acre lane, and tubes carried thereby forming t e lateral terminals of said. aeroplane, said tubes be ing oval in crosssection, with their longer axes substantiall Y horizontal and open from end to end for ree movement of air therethrough.

14. In an aeroplane, the combination of: a direction rudder of an elevating rudder connected to sai direction rudder to turn horizontally therewith and located back thereof, and separate means for actuating the said rudders to respectively change the direction of flight and the elevation of the aeroplane. r

15. In an aeroplane the combination with V a direction rudder, oi an elevating rudder,

an auxiliary frame carrying the said elevating rudder and connected to move with said direction rudder, a wheel, connections between said wheel and said elevating plane to efi'ect upward movement of the aeroplane when the wheel shaft is pulled up, and downward movement of the aeroplane when the wheel shaft is pushed down, and separate means to efiect the operation of the direction rudder. a

16., In an aeroplane, the combination with tubes for the passage of air therethrough,

mes es said tubes to operate at will only the sections of any one of said tubes at a time, and means for operating only some of the sections of any one tube at a time.

17. In an aeroplane, the combination with balancing tubes each having four longitudinal movable sections and fixed upper and lower sections, of a lever and CODRGGlJlOIlS for simultaneously moving all the sections of all the tubes toward horizontal positions thereby opening the tubes laterally, additional mechanism for efiecting the opening of any one tube laterally, and means for only partially opening any one tube laterally.

18, In an aeroplane, the combination with a supporting (plane, of unobstructed tubes at the outer e ges of the supporting plane, portions of each of said tubes being rigidly supported and other portions of eachtube being hinged to said rigidly supported portions, springs normally maintaining said hinged portions in normal positions, and manually operable means connected to said hinged portions and adapted to swing the latter from their normal ositions.

In testimony whereof have signed my name to this specification, in the presence of two subscribing witnesses.

snares L. MARENESS.

. Witnesses: NINA J. Hersnn, C. H. SEEM. 

